System And Method Of Continuous Detonation In A Gas Turbine Engine

Abstract

A continuous detonation system, including: a rotatable member including a forward end, an aft end, a circumferential wall and a longitudinal centerline axis extending therethrough; an outer circumferential wall, wherein the rotatable member is positioned therein so that the circumferential wall of the rotatable member is spaced radially inwardly from the outer circumferential wall; at least one helical channel formed by a plurality of helical sidewalls extending between the circumferential wall of the rotatable member and the outer circumferential wall, each helical channel being open at the forward end and the aft end of the rotatable member so as to provide flow communication therethrough; an air supply for providing air to each helical channel; and, a fuel supply for providing fuel to each helical channel. In this way, a mixture of the fuel and air is continuously detonated within each helical channel in a manner such that combustion gases exit therefrom with an increased pressure and temperature.

Description

CROSS-REFERENCE TO RELATED APPLICATION[0001]The present application is related to an application entitled “Axially Suspended Detonation Combustor For A Gas Turbine Engine,” having Ser. No. ______, which is filed concurrently herewith and is owned by the assignee of the present invention.BACKGROUND OF THE INVENTION[0002]The present invention relates generally to a system and method of continuous detonation in a gas turbine engine and, in particular, to a system and method of continuous detonation in a gas turbine engine where a mixture of fuel and air is continuously detonated in at least one helical channel of a rotatable member to form combustion gases having an increased pressure and temperature.[0003]It is well known that typical gas turbine engines are based on the Brayton Cycle, where air is compressed adiabatically, heat is added at constant pressure, the resulting hot gas is expanded in a turbine, and heat is rejected at constant pressure. The energy above that required to dr...

AI Technical Summary

Problems solved by technology

While engines based on the Brayton Cycle have reached a high level of thermodynamic efficiency by steady improvements in component efficiencies and increases in pressure ratio and peak temperature, further improvements are becoming increasingly costly to obtain.

While such pulse detonation configurations have advanced the state of the art, the valves and associated actuators are subjected to very high temperatures and pressures.

This not only presents a reliability problem, but can also have a detrimental effect on the turbomachinery of the engine.

Other obstacles include the prevention of backflow into the lower pressure regions upstream of the pulse detonator, survivability of turbomachinery and ductwork upstream and downstream of the pulse detonator in an axially unsteady flow field, and capability of cooling flows for maintaining a positive gradient during pulses.

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